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    METHOD OF CONTROLLING AN AIRCRAFT ELECTRICAL POWER GENERATION SYSTEM
    11.
    发明申请
    METHOD OF CONTROLLING AN AIRCRAFT ELECTRICAL POWER GENERATION SYSTEM 审中-公开
    控制飞机电力发电系统的方法

    公开(公告)号：US20140125121A1

    公开(公告)日：2014-05-08

    申请号：US14036721

    申请日：2013-09-25

    Applicant: ROLLS-ROYCE PLC

    Inventor： Huw Llewelyn EDWARDS ,  Parag VYAS ,  Malcolm Laurence HILLEL ,  Alasdair GARDNER ,  Sean Patrick ELLIS ,  Nicholas HOWARTH

    IPC: B60R16/03

    CPC classification number: B60R16/03 ,  B64D2221/00 ,  H02J4/00 ,  H02J7/1446 ,  Y02T50/54

    Abstract: A method of operating an electrical power generation system on an aircraft. The method includes assessing a required electrical power of the aircraft, assessing whether a first and a second electrical power source are able to provide the required electrical power in combination, assessing a predetermined condition, determining an operating mode of the first and second electrical power sources to match the predetermined condition, and operating the first and second electrical power sources according to the determined operating mode.

    Abstract translation: 一种在飞机上操作发电系统的方法。 该方法包括评估飞行器的所需电力，评估第一和第二电源是否能够组合提供所需的电力，评估预定条件，确定第一和第二电源的操作模式 以匹配预定条件，并且根据所确定的操作模式操作第一和第二电源。

    GEARED GAS TURBINE ENGINE
    12.
    发明申请
    GEARED GAS TURBINE ENGINE 有权

    公开(公告)号：US20220412269A1

    公开(公告)日：2022-12-29

    申请号：US17731877

    申请日：2022-04-28

    Applicant: ROLLS-ROYCE PLC

    Inventor： Nicholas HOWARTH ,  Gareth M. ARMSTRONG

    IPC: F02C7/36 ,  F02C3/113 ,  F01D15/12

    Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

    GAS TURBINE ENGINE COMPRESSION SYSTEM
    15.
    发明申请
    GAS TURBINE ENGINE COMPRESSION SYSTEM 审中-公开

    公开(公告)号：US20200290743A1

    公开(公告)日：2020-09-17

    申请号：US16437284

    申请日：2019-06-11

    Applicant: ROLLS-ROYCE plc

    Inventor： Gareth M ARMSTRONG ,  Nicholas HOWARTH

    IPC: B64D27/10 ,  F02C3/06 ,  F02K3/06

    Abstract: A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

    GAS TURBINE ENGINE
    16.
    发明申请
    GAS TURBINE ENGINE 审中-公开
    气体涡轮发动机

    公开(公告)号：US20160040605A1

    公开(公告)日：2016-02-11

    申请号：US14797871

    申请日：2015-07-13

    Applicant: ROLLS-ROYCE PLC

    Inventor： Nicholas HOWARTH

    IPC: F02C9/18 ,  F02C3/04

    Abstract: A gas turbine engine including a compressor, a turbine having one or more stages and a combustor, the combustor being located between the compressor and turbine. The gas turbine engine further includes a bleed from a core defined by a core duct, the core duct surrounding and extending between the turbine and combustor at least. The bleed includes at least one inlet located downstream of the combustor and upstream of at least one of the turbine stages. The turbine is arranged in use to drive the compressor. The bleed is arranged to be controllable in use to selectively bleed air from the core through the inlet and to thereby control the power delivered by the turbine to the compressor.

    Abstract translation: 一种燃气涡轮发动机，其包括压缩机，具有一个或多个级的涡轮机和燃烧器，所述燃烧器位于压缩机和涡轮机之间。 燃气涡轮发动机还包括从由核心管道限定的芯的渗出物，至少在涡轮和燃烧器之间包围和延伸的芯管。 渗流包括位于燃烧器下游的至少一个入口和至少一个涡轮级的上游。 涡轮机布置在使用中以驱动压缩机。 排放物布置成在使用中是可控的，以选择性地将空气从芯通过入口排出，并由此控制由涡轮机输送到压缩机的功率。

    AIR INTAKE AND A METHOD OF CONTROLLING THE SAME
    17.
    发明申请
    AIR INTAKE AND A METHOD OF CONTROLLING THE SAME 有权
    空气摄入及其控制方法

    公开(公告)号：US20140311580A1

    公开(公告)日：2014-10-23

    申请号：US14221936

    申请日：2014-03-21

    Applicant: ROLLS-ROYCE PLC

    Inventor： Nicholas HOWARTH

    IPC: F02C7/057

    CPC classification number: F02C7/057 ,  F02C7/042 ,  F05D2220/80 ,  F05D2250/141 ,  F05D2260/407 ,  F05D2300/501 ,  Y02T50/672 ,  Y10T137/0379 ,  Y10T137/0536 ,  Y10T137/0645

    Abstract: An air intake guide for a jet propulsion power plant for a supersonic aircraft comprises an intake aperture, an intake centre body and an intake adjustment device.The intake aperture has an intake lip, an intake centre body is positioned within the aperture, and an intake adjustment device is positioned on a radially inwardly facing surface of the air intake guide downstream of the intake lip.The intake adjustment device comprises a flexible panel and an actuator with the actuator being adapted to deflect the flexible panel in a radially inwardly direction so as to reduce a cross-sectional area of the intake aperture and thereby to position a shock wave at the intake lip.

    Abstract translation: 用于超音速飞行器的喷气式推进动力装置的进气引导件包括进气孔，进气中心体和进气调节装置。 入口孔具有进气口，进气中心体位于孔内，进气调节装置位于进气口下游进气口径向向内的表面上。 进气调节装置包括柔性面板和致动器，致动器具有适于使柔性板沿径向向内的方向偏转，以便减小进气孔的横截面面积，从而将冲击波定位在进气口 。

    GEARED GAS TURBINE ENGINE
    18.
    发明申请
    GEARED GAS TURBINE ENGINE 有权

    公开(公告)号：US20250012221A1

    公开(公告)日：2025-01-09

    申请号：US18785906

    申请日：2024-07-26

    Applicant: ROLLS-ROYCE plc

    Inventor： Nicholas HOWARTH ,  Gareth M Armstrong

    IPC: F02C7/36 ,  F01D15/12 ,  F02C3/113

    Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

    ROTARY ASSEMBLY
    20.
    发明公开
    ROTARY ASSEMBLY 审中-公开

    公开(公告)号：US20240151154A1

    公开(公告)日：2024-05-09

    申请号：US18379976

    申请日：2023-10-13

    Applicant: ROLLS-ROYCE plc

    Inventor： Christopher A MURRAY ,  Nicholas HOWARTH

    IPC: F01D17/16

    CPC classification number: F01D17/162 ,  F05D2260/90 ,  F05D2270/335

    Abstract: A rotary assembly for driving spool rotation includes a rotor and a flow modifier. The rotor is mechanically coupled to a spool of a gas turbine engine. The flow modifier receives flow from and/or direct flow to the rotor. The rotary assembly permits relative movement between the rotor and the flow modifier to move between: a turbine configuration wherein the rotor receives air from an external air source to drive the spool to rotate; and a compressor configuration wherein the rotor is driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system. The rotary assembly also includes controller to control relative movement between the rotor and the flow modifier through a range of turbine positions of the turbine configuration to vary a torque applied to the rotor for driving the spool.

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